CN114807790A - Radiation-resistant layered composite material for satellite devices and preparation method thereof - Google Patents
Radiation-resistant layered composite material for satellite devices and preparation method thereof Download PDFInfo
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Abstract
The application discloses a radiation-resistant layered composite material for a satellite device and a preparation method thereof, wherein the method comprises the following steps: respectively carrying out acid-base treatment on the 2A12 aluminum alloy, the intermediate layer alloy and the tantalum layer material to remove surface oil stains and the like; stacking the three layers of materials together according to the sequence of 2A12 aluminum alloy layer, middle layer alloy and tantalum layer, and fixing by spot welding; rolling and compounding the spot-welded material through a cold rolling mill; and carrying out annealing heat treatment on the compounded material, and then flattening and trimming. The composite material prepared by the method has stable performance, low cost and easy maintenance, has better shielding effect than a simple substance metal material, and can reduce the quality and cost of electronic devices. The cold rolling compounding method is adopted, the surface quality and the precision are good, the corrosion and the oxidation of the tantalum material can be avoided, and an intermetallic compound layer which can damage the interface bonding strength can not be generated.
Description
Technical Field
The application relates to the technical field of satellite devices, in particular to an anti-radiation laminated composite material for a satellite device and a preparation method thereof.
Background
Because the satellite can encounter the radiation of various space charged particles, the space radiation resistance of the electronic device is an important factor influencing the development of medium and high orbit satellites and deep space exploration satellites in navigation, communication and the like. Currently, protection of electronic devices from the effects of total dose and displacement damage is primarily by passive shielding.
The radiation-resistant shielding technology is a radiation protection technology adopted for enabling devices for spacecrafts and other satellites to normally work in a space radiation environment, and is a key basic technology which is related to the in-orbit survival capability of the satellites and ensures high reliability and long service life of the satellites. The radiation-resistant shielding protection of the satellite device shell mainly adopts elemental metal materials such as aluminum and tantalum to carry out local shielding, but the shielding effect of the elemental metal materials is limited, and the method for improving the radiation protection effect can only increase the thickness of a shielding layer, so that huge pressure and unsustainable quality cost are brought to the radiation-resistant design of single-machine equipment.
The material of the existing electronic device is an aluminum/tantalum laminar composite material used for meeting the radiation-resistant reinforcement requirement of the satellite, but because the strength of the two materials is too high, the shearing stress generated in the cold rolling process is difficult to cause the interface to generate good bonding; although effective bonding of the interface can be achieved using hot-roll compounding, aluminum/tantalum materials can produce intermetallic compounds under high temperature conditions that can result in a dramatic reduction in the interface bond strength.
Disclosure of Invention
In order to solve the defects in the field, the application provides a radiation-resistant layered composite material for a satellite device and a preparation method thereof.
According to one aspect of the application, a preparation method of the radiation-resistant layered composite material for the satellite device is provided, and comprises the following steps:
respectively carrying out acid-base treatment on the 2A12 aluminum alloy, the intermediate layer alloy and the tantalum layer material to remove surface oil stains and the like;
stacking the three layers of materials according to the sequence of 2A12 aluminum alloy, the middle layer and tantalum, and fixing by spot welding;
rolling and compounding the spot-welded material through a cold rolling mill;
and carrying out annealing heat treatment on the compounded material, and then flattening and trimming.
According to some embodiments of the present application, the interlayer alloy is selected from a 1-series alloy or a 3-series alloy.
Further, the composition of the interlayer alloy comprises: 0.3-0.6 part of Si, 0.05-0.1 part of Zr, 0.05-0.1 part of Yb, less than or equal to 0.1 part of Fe, less than or equal to 0.05 part of Cu, less than or equal to 0.05 part of Mn, less than or equal to 0.05 part of Mg, less than or equal to 0.05 part of Zn, and the balance of aluminum and inevitable impurity elements.
According to some embodiments of the present application, the cold rolling has a rolling deformation of 45% to 50%.
According to some embodiments of the application, the annealing temperature is: 450 ℃ and 550 ℃; the heat preservation time is as follows: 40-50 h.
According to another aspect of the application, the radiation-resistant layered composite material for the star device is a 2A 12/interlayer alloy/Ta composite material.
The 2A12 aluminum alloy is a high strength hard aluminum that can be heat treated for strengthening.
According to some embodiments of the present application, the interlayer alloy is selected from a 1-series alloy or a 3-series alloy.
Further, the composition of the interlayer alloy comprises: 0.3-0.6 part of Si, 0.05-0.1 part of Zr, 0.05-0.1 part of Yb, less than or equal to 0.1 part of Fe, less than or equal to 0.05 part of Cu, less than or equal to 0.05 part of Mn, less than or equal to 0.05 part of Mg, less than or equal to 0.05 part of Zn, and the balance of aluminum and inevitable impurity elements.
According to some embodiments of the present application, the interlayer alloy thickness comprises 1-4% of the total composite thickness;
further, the interlayer alloy thickness accounts for 3% of the total composite thickness.
Compared with the prior art, the application at least comprises the following beneficial effects:
according to the embodiment of the application, the preparation method of the radiation-resistant layered composite material for the satellite device is provided, and the surface quality and precision of the composite material are superior to those of hot rolling compounding by adopting a cold rolling compounding method; because the cold rolling compounding does not need preheating, the temperature of the tantalum is raised by the generated deformation heat to be over 200 ℃, the tantalum is not oxidized, and an intermetallic compound layer which can damage the interface bonding strength is not generated.
The interlayer alloy is added into the layered composite material, so that the strength is low, the ductility is good, enough deformation can be generated in the cold rolling process, the combination effect of 2A12 and Ta can be improved, and the problem of difficult interface recombination caused by shear stress generated in the cold rolling process is solved; in addition, the thickness of the intermediate layer alloy adopted by the composite material is thin, only accounts for about 3% of the total thickness of the composite material, and the influence on the mechanical property is negligible.
The application also provides a radiation-resistant layered composite material for the satellite device prepared by the method, which is a 2A 12/intermediate layer alloy/Ta three-layer composite material. Compared with the existing elemental metal material, the composite material has stable high-energy electron radiation resistance, low preparation cost, easy maintenance and better shielding effect than the elemental metal material, and can reduce the quality and cost of electronic devices.
This application intermediate layer alloy and tantalum layer are when high temperature heat treatment, because the effect of the compound microalloying in interface, can restrain interdiffusion between the tantalum aluminium, slow down the formation of interface tantalum aluminium brittle compound, and thick continuous tantalum aluminium intermetallic brittle compound can not be generated at the interface, so can effectively avoid the separation of aluminium tantalum laminar composite interface, when guaranteeing aluminium tantalum laminar composite high temperature heat treatment, the interface combines firmly.
Drawings
Fig. 1 is a schematic view of a radiation-resistant layered composite according to an exemplary embodiment of the present application.
Fig. 2 is a scanning electron microscope image of the radiation-resistant layered composite material of the exemplary embodiment of the present application after heat treatment at 550 ℃.
FIG. 3 is a scanning electron micrograph of the composite material of comparative example 4 of the present application after heat treatment.
Detailed Description
As mentioned above in the background, current shielding will impose a great pressure on the radiation-resistant design of stand-alone equipment and an intolerable quality cost. Although the shielding protection by adopting the composite material can improve the protection effect and save the cost, the preparation of the composite material still has great problems. Aiming at the problems, the application provides a radiation-resistant layered composite material for a satellite device and a preparation method thereof.
The technical solutions of the present application will be described clearly and completely with reference to the embodiments of the present application, and it should be understood that the described embodiments are some, but not all, embodiments of the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
It is specifically noted that similar alternatives and modifications will be apparent to those skilled in the art for the present application, which are all considered to be included in the present application. It will be apparent to the skilled artisan that modifications, variations or appropriate alterations and combinations of the methods and applications described herein may be made to implement and apply the techniques of the present application without departing from the content, spirit and scope of the application. It is to be understood that the embodiments described are only a few embodiments of the present application and not all embodiments.
If the specific conditions are not indicated, the method is carried out according to the conventional conditions or the conditions suggested by the manufacturer, and the raw material medicines or auxiliary materials and the reagents or instruments used by the method are conventional products which can be obtained commercially.
The present application is described in detail below.
The current shielding protection will bring huge pressure and intolerable quality cost to the radiation-resistant design of the single-machine equipment. The application finds that the aluminum/tantalum composite material is used for shielding protection, and the problems can be effectively solved.
Based on the above, the application provides a radiation-resistant layered composite material for a satellite device, which is a 2A 12/middle layer/Ta three-layer composite material.
The elemental metal aluminum has a limited radiation-resistant effect, and for the protection of some high-energy electron radiation, the radiation-resistant capability can be improved only by increasing the thickness, but the quality is increased by increasing the thickness, and the cost for increasing the quality of a satellite is very high.
Wherein the interlayer alloy is selected from: one of a 1-series aluminum alloy and a 3-series aluminum alloy.
Further, the composition of the interlayer alloy comprises: 0.3-0.6 part of Si, 0.05-0.1 part of Zr, 0.05-0.1 part of Yb, less than or equal to 0.1 part of Fe, less than or equal to 0.05 part of Cu, less than or equal to 0.05 part of Mn, less than or equal to 0.05 part of Mg, less than or equal to 0.05 part of Zn, and the balance of aluminum and inevitable impurity elements.
The thickness of the intermediate layer alloy accounts for 1-4% of the total thickness of the composite material; alternatively, it is about 3%.
The intermediate layer alloy selected by the method is low in strength and good in ductility, and can generate enough deformation in the cold rolling process, so that the 2A12/1 or 3 series aluminum alloy/Ta three-layer composite material with good combination effect is prepared. Other alloys having the same properties as the intermediate layer are within the scope of the present application.
The conventional aluminum/tantalum laminated composite material is generally prepared by a hot rolling compounding method, but in the laminated composite material of the application, 2A12 aluminum alloy is used as the aluminum material, and pure tantalum is used as the tantalum.
The present application has also found that the above-mentioned composite material, if hot-rolled compounding is used, will have the following disadvantages:
(1) during hot rolling and compounding, although effective combination of an interface can be realized, intermetallic compounds can be generated in the aluminum/tantalum material under a high-temperature condition, and the compound can cause the interface combination strength to be reduced sharply, so that the composite material is damaged by layering;
(2) in the hot rolling process, the general hot rolling temperature is above 350 ℃, and the temperature can exceed 450 ℃ by adding the deformation heat in the compounding process. However, if the temperature of pure tantalum exceeds 280 ℃, oxidation reaction begins to occur, and when the temperature exceeds 350 ℃, the tantalum material shows obvious corrosion oxidation reaction, the surface begins to discolor, the performance is reduced, and more serious oxidation corrosion can occur.
Therefore, the radiation-resistant layered composite material for the satellite device adopts a cold rolling composite preparation method.
However, the tensile strength of the 2A12 aluminum alloy and the pure tantalum material at normal temperature exceeds 400MPa, and the shear stress generated in the cold rolling process of the two materials is difficult to cause good bonding of the interface because the strength is too high.
The radiation-resistant material for the satellite device has high requirements on interface bonding strength and surface quality, the performance requirements are difficult to meet by adopting the traditional cold rolling or hot rolling compounding, and the production difficulty and cost can be greatly increased if the atmosphere-protected hot rolling is used.
Based on the above problems, the present application provides a method for preparing the radiation-resistant layered composite material for the satellite device, which comprises the following steps:
(1) respectively carrying out acid-base treatment on the 2A12 aluminum alloy, the intermediate layer alloy (1 series or 3 series alloy) and the tantalum layer material to remove oil stains on the surface;
(2) stacking the three layers of materials according to the sequence of 2A12 aluminum alloy, the middle layer and tantalum, and fixing by spot welding;
(3) rolling and compounding the spot-welded material by a cold rolling mill, wherein the rolling deformation is 45-50%;
cold rolling composite parameters: rolling temperature: room temperature; rolling speed: 1 m/min;
(4) and (3) annealing the compounded material at the temperature of 450-550 ℃, and then flattening and trimming.
This application adopts cold rolling complex, avoids the too high corrosion oxidation that produces tantalum of hot rolling temperature to and influence interface bonding strength's intermetallic compound's formation between aluminium tantalum, still through adding intermediate layer alloy material, avoids the difficult problem of complex that the shear stress of cold rolling process leads to.
According to some embodiments of the present application, as shown in FIG. 2, the composite material of the present application is free of intermetallic compounds at a holding time of up to 550 deg.C/48 h. The interface bonding strength of the composite material is 25-35N/mm.
The present application will be described in detail with reference to specific examples.
Example 1
2A 12/intermediate layer/Ta three-layer composite material of the present application
(1) Respectively carrying out acid-base treatment on the 2A12 aluminum alloy, the 1050 alloy and the tantalum layer material to remove oil stains on the surface and the like;
(2) stacking the three layers of materials according to the sequence of 2A12 aluminum alloy, 1050 alloy and tantalum, and fixing by spot welding;
(3) rolling and compounding the spot-welded material through a cold rolling mill, wherein the rolling deformation is 45%;
rolling temperature: room temperature; rolling speed: 1 m/min;
(4) and (3) carrying out annealing heat treatment at 500 ℃ on the compounded material, keeping the temperature for 50 hours, and then flattening and trimming.
Interface bonding strength test: 30N/mm.
Example 2
2A 12/intermediate layer/Ta three-layer composite of the present application
(1) Respectively carrying out acid-base treatment on the 2A12 aluminum alloy, the 1060 alloy and the tantalum layer material to remove oil stains on the surface;
(2) stacking the three-layer materials according to the sequence of 2A12 aluminum alloy, 1060 alloy and tantalum, and fixing by spot welding;
(3) rolling and compounding the spot-welded material through a cold rolling mill, wherein the rolling deformation is 50%;
(4) and (3) annealing heat treatment is carried out on the compounded material at 550 ℃, heat preservation is carried out for 48 hours, and then leveling and trimming are carried out.
Interface bonding strength test: 35N/mm.
Example 3
2A 12/intermediate layer/Ta three-layer composite material of the present application
(1) Respectively carrying out acid-base treatment on the 2A12 aluminum alloy, the industrial pure aluminum and the tantalum layer material to remove oil stains on the surface and the like;
(2) stacking the three layers of materials according to the sequence of 2A12 aluminum alloy, industrial pure aluminum and tantalum, and fixing by spot welding;
(3) rolling and compounding the spot-welded material by a cold rolling mill, wherein the rolling deformation is 43%;
(4) and (3) annealing and heat treating the compounded material at 490 ℃, preserving heat for 50h, and then flattening and trimming.
(5) Interface bonding strength test: 25N/mm.
Comparative example 1
At present, the single-substance aluminum alloy shielding layer is commonly used for devices for the satellite.
Metal aluminum is widely used in radiation protection because of its good mechanical properties and low economic cost. To achieve a total radiation dose of less than 100krad [ Si ] encountered in 15 years of rail under 3mm aluminum shielding for an electronic device, the GEO and MEO rails require 5mm and 7mm aluminum materials for shielding, respectively; for deep space Jupiter detection, the total dose of radiation is as high as nearly 200krad [ Si ] even under a 20mm thick elemental Al shield due to the higher electron energy. This would put a great strain on the radiation-resistant design of stand-alone equipment and unacceptable mass costs.
Comparative example 2
Pure aluminum/Ta double-layer composite material
The preparation method is the same as example 1.
As a result: the strength of the double-layer composite material is lower than or equal to 10N/mm, and the strength requirement of a satellite device cannot be met; at the same time, the interface between tantalum and aluminum generates coarse and continuous tantalum-aluminum intermetallic brittle compounds, causing aluminum layer/tantalum layer separation.
Comparative example 3
2A12/Ta two-layer composite material without interlayer alloy
The preparation method is the same as example 1.
As a result: the interface bonding strength is lower than or equal to 3N/mm, and the composition is not realized, so that the method can not be applied to satellite devices.
Comparative example 4
The preparation method of the aluminum-tantalum composite plate in the prior art comprises the following steps:
(1) after the tantalum plate belt is pretreated, one side surface of the tantalum plate belt is electroplated with silver to obtain a tantalum plate belt blank with a silver coating;
the specific process of the pretreatment is as follows: firstly carrying out alkali washing on the tantalum plate strip, then carrying out acid washing, loading voltage while carrying out acid washing by taking the tantalum plate strip as an anode and taking a tank body of an electrolytic tank as a cathode, carrying out electrolytic activation on the tantalum plate strip, and finally carrying out hydrogen heating reduction treatment
(2) Carrying out hot rolling compounding on the tantalum plate strip blank on the silver plating side and the aluminum plate base material to obtain a tantalum-aluminum composite plate strip; in the hot rolling compounding process, the temperature of hot rolling compounding is 250-450 ℃, the rolling speed is 5-10 m/min, and the first pass processing rate of hot rolling compounding is 25-50%;
(3) after the tantalum-aluminum composite plate strip is subjected to a heat treatment process, obtaining the tantalum-aluminum composite plate strip for the capacitor; the heat treatment process sequentially comprises an annealing process and a cold rolling process; in the annealing process, the temperature of the annealing treatment is 350-450 ℃, and the time of the annealing treatment is 8-15 h; in the cold rolling process, the cold rolling temperature is 150-250 ℃, the cold rolling speed is 100m/min, and the first time working rate of the cold rolling is 20-35%.
As a result: the heat treatment temperature of the material is only 450 ℃ at most, and obvious intermetallic compounds are generated (see figure 3). After hot rolling, the interface bonding strength is 12-15N/mm.
The composite material of the application has no generation of intermetallic compounds (figure 2), and the interface bonding strength is high and can reach 25-35N/mm. In contrast, the composite material of comparative example 4, as seen by scanning electron microscopy (fig. 3), has significant intermetallic compound formation affecting the interfacial bonding strength.
The above description of the embodiments is only intended to help understand the method of the present application and its core ideas. It should be noted that, for those skilled in the art, it is possible to make several improvements and modifications to the present application without departing from the principle of the present application, and such improvements and modifications also fall within the scope of the claims of the present application.
Claims (8)
1. A preparation method of a radiation-resistant layered composite material for a satellite device is characterized by comprising the following steps:
respectively carrying out acid-base treatment on the 2A12 aluminum alloy, the intermediate layer alloy and the tantalum material to remove surface oil stains and the like;
stacking the three layers of materials together according to the sequence of 2A12 aluminum alloy layer, middle layer and tantalum layer, and fixing by spot welding;
rolling and compounding the spot-welded material through a cold rolling mill;
and carrying out annealing heat treatment on the compounded material, and then flattening and trimming.
2. The method according to claim 1, wherein the interlayer alloy is selected from a 1-series alloy or a 3-series alloy.
3. The method of claim 1, wherein the composition of the interlayer alloy comprises: 0.3-0.6 part of Si, 0.05-0.1 part of Zr, 0.05-0.1 part of Yb, less than or equal to 0.1 part of Fe, less than or equal to 0.05 part of Cu, less than or equal to 0.05 part of Mn, less than or equal to 0.05 part of Mg, less than or equal to 0.05 part of Zn, and the balance of aluminum and inevitable impurity elements.
4. The method of claim 3, wherein the cold rolling has a rolling deformation of 45-50%.
5. The method of claim 4, wherein the annealing temperature is: 450 ℃ and 550 ℃; the heat preservation time is as follows: 40-50 h.
6. A radiation-resistant layered composite for a satellite device prepared by the method of any one of claims 1 to 5.
7. The composite of claim 6, wherein the interlayer alloy thickness is 1-4% of the total composite thickness.
8. The composite of claim 6, wherein the interlayer alloy thickness comprises 3% of the total composite thickness.
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| JPWO2017018514A1 (en) * | 2015-07-29 | 2018-05-24 | 新日鐵住金株式会社 | Titanium composite and titanium material for hot rolling |
| CN109732087A (en) * | 2019-01-28 | 2019-05-10 | 中南大学 | A kind of preparation method of powder metallurgy Ti-Ta binary metal-metal-based layer-shaped composite material |
| CN110420999A (en) * | 2019-05-20 | 2019-11-08 | 重庆大学 | A kind of titanium/aluminium laminated composite plate preparation method of pre- cold rolling diffusion |
| CN110340174A (en) * | 2019-07-12 | 2019-10-18 | 南京工程学院 | A kind of production method of capacitor tantalum aluminum composite panel belt |
| CN113352708A (en) * | 2021-07-06 | 2021-09-07 | 华北电力大学 | Light high-strength Mg-Ta composite metal plate and room-temperature rolling forming method thereof |
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